CN209305826U - A kind of culvert vertical take-off and landing unmanned aerial vehicle - Google Patents
A kind of culvert vertical take-off and landing unmanned aerial vehicle Download PDFInfo
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- CN209305826U CN209305826U CN201821801590.8U CN201821801590U CN209305826U CN 209305826 U CN209305826 U CN 209305826U CN 201821801590 U CN201821801590 U CN 201821801590U CN 209305826 U CN209305826 U CN 209305826U
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- fuselage
- cavity
- fixedly connected
- duct
- unmanned aerial
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Abstract
The utility model discloses a kind of culvert vertical take-off and landing unmanned aerial vehicles, including fuselage, the two sides of the fuselage are symmetrically arranged with two wings, the fuselage is far from being symmetrically arranged with two empennages on one end of wing, the second duct of horizontal direction is equipped on two wings, the first duct of vertical direction is equipped at the center of the fuselage, duct engine is equipped in first duct and the second duct, the bottom side of the fuselage is equipped with front buffer device, the front buffer device is arranged far from empennage, the bottom side of two wings is equipped with postposition damping device, two postposition damping devices are close to fuselage and are symmetrical set.The utility model can be effectively solved the problem of being likely to occur rollover because of fuselage inclination during aircraft lands, the posture that can be landed to aircraft is corrected, and buffering and elimination that generated vibration in the process carries out high degree can be landed to aircraft.
Description
Technical field
The utility model relates to unmanned vehicle technical field more particularly to a kind of culvert vertical take-off and landing unmanned aerial vehicles.
Background technique
Unmanned vehicle is the not manned vehicle manipulated using radio robot and the presetting apparatus provided for oneself,
By feat of be not necessarily to driver the characteristics of, compared with manned aircraft, it have small in size, low cost, it is easy to use, to operational environment
It is required that the advantages that low, battlefield survival is stronger.Existing unmanned vehicle usually realizes VTOL by setting duct,
Because requirement of the VTOL to landing environment is small.
Existing culvert vertical take-off and landing unmanned aerial vehicle, because the landing modes of VTOL are taken, in landing
In the process, if ambient enviroment has wind, aircraft is easy to be affected by the wind and tilt, or even rollover, in addition, aircraft and ground
Vibration can be generated during face contact, has significant damage to the electronic equipment of aircraft interior.
Summary of the invention
Purpose of the utility model is to solve disadvantages existing in the prior art, such as: existing culvert vertical take-off and landing
Unmanned vehicle during landing, if ambient enviroment has wind, flies because taking the landing modes of VTOL
Row device is easy to be affected by the wind and tilt, or even rollover, in addition, vibration can be generated in aircraft and ground contact process, it is right
The electronic equipment of aircraft interior has significant damage.
To achieve the goals above, the utility model adopts the technical scheme that
A kind of culvert vertical take-off and landing unmanned aerial vehicle, including fuselage, the two sides of the fuselage are symmetrically arranged with two wings, institute
Fuselage is stated far from two empennages are symmetrically arranged on one end of wing, second that horizontal direction is equipped on two wings is contained
Road is equipped with the first duct of vertical direction at the center of the fuselage, is equipped with duct in first duct and the second duct
Engine, the bottom side of the fuselage are equipped with front buffer device, and the front buffer device is arranged far from empennage, two machines
The bottom side of the wing is equipped with postposition damping device, and two postposition damping devices are close to fuselage and are symmetrical set.
Preferably, the front buffer device includes support rod, and the support rod is fixedly connected on the bottom side of fuselage, described
One end of support rod is fixedly connected with mounting plate, and the two sides of the mounting plate are fixedly connected to two symmetrically arranged fixture blocks,
It is fixedly connected with the fixed link through fixture block between two opposite fixture blocks, is rotatably connected to connection in the fixed link
Bar, the two sides of the connecting rod are fixedly connected to torsional spring, and the torsional spring is fixedly connected on fixture block far from one end of connecting rod,
Elastic telescopicing rod is rotatably connected to by symmetrically arranged limited block between two connecting rods, the connecting rod is far from fixture block
One end front-wheel is installed.
Preferably, the postposition damping device includes damper, and the damper is fixedly connected on the bottom side of wing, described
The first cavity and the second cavity are equipped in damper, by through-hole connection between first cavity and the second cavity, described the
Piston is slidably connected in one cavity, and the mandril through damper, the top are fixedly connected at the center of the piston bottom side
Bar is equipped with rear-wheel far from one end of piston, is fixedly connected with spring on the downside wall of second cavity, and the one of the spring
End is fixedly connected with sliding block, and the sliding block is slidably connected in the second cavity.
Preferably, restraining position ring block is fixedly connected on the inner sidewall of second cavity, the stop collar is arranged close to through-hole.
Preferably, the front wheels and rear wheels are wear-resisting rubber wheel.
Preferably, the surface of the piston and sliding block is equipped with rubber membrane.
In the utility model, the beneficial effects of the utility model are:
1, when fuselage in descent because context has wind, influenced by wind-force and when run-off the straight, it is fast in fuselage
The moment to be fallen to the ground, because of the inclination of fuselage, one of them in two front-wheels is in contact with ground first, in fuselage
Gravity under, the connecting rod being rotatablely connected with the front-wheel that ground first contacts is rotated around fixed link, drive torsional spring turn
Dynamic, the elastic force that torsional spring generates reacts on connecting rod, gives one in rotational direction opposite elastic force of connecting rod, hinders connecting rod
It continues around fixed link to be rotated, elastic force acts on ground through connecting rod and front-wheel, the slope trend of fuselage is hindered, in addition, even
Extension bar will drive elastic telescopicing rod elongation during rotation, to play the work of damping by the elastic force of elastic telescopicing rod
With.
2, the moment that fuselage is fallen to the ground, rear-wheel and ground face contact, fuselage force wing to drive damping under the effect of gravity
Device moves down, and mandril and piston are moved up with respect to the first cavity, and under the extruding of piston, the air in the first cavity is through logical
Hole flows into the second cavity, and the first cavity and the indoor air pressure of the second cavity chamber increase, and air is compressed, connect to rear-wheel and ground
Vibration caused by during touching carries out preliminary damping, and the air pressure for converting vibration in the first cavity and the second cavity becomes
Change, with the increase of air pressure, when air is greater than spring to sliding block to the gravity of the pressure and sliding block itself of sliding block in second chamber
Elastic force when, sliding block is moved down along the inner sidewall of the second cavity, and spring is compressed, and the elastic force of spring hinders the movement of sliding block simultaneously
It is buffered, further progress damping.
Detailed description of the invention
Fig. 1 be the utility model proposes a kind of culvert vertical take-off and landing unmanned aerial vehicle side view；
Fig. 2 be the utility model proposes a kind of culvert vertical take-off and landing unmanned aerial vehicle top view；
Fig. 3 is the enlarged drawing of A structure in Fig. 1；
Fig. 4 be the utility model proposes a kind of culvert vertical take-off and landing unmanned aerial vehicle front buffer device front knot
Structure schematic diagram；
Fig. 5 be the utility model proposes a kind of culvert vertical take-off and landing unmanned aerial vehicle shock absorber section structural representation
Figure.
In figure: 1 fuselage, 2 wings, 3 empennages, 4 first ducts, 5 second ducts, 6 support rods, 7 connecting rods, 8 front-wheels, 9 subtract
Shake device, 10 mandrils, 11 rear-wheels, 12 mounting plates, 13 fixture blocks, 14 fixed links, 15 torsional springs, 16 limited blocks, 17 elastic telescopicing rods, 18 the
One cavity, 19 second cavitys, 20 pistons, 21 sliding blocks, 22 stop collars, 23 springs.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.
In the description of the present invention, it should be understood that term " on ", "lower", "front", "rear", "left", "right",
The orientation or positional relationship of the instructions such as "top", "bottom", "inner", "outside" is to be based on the orientation or positional relationship shown in the drawings, and is only
For ease of description the utility model and simplify description, rather than the device or element of indication or suggestion meaning must have it is specific
Orientation, be constructed and operated in a specific orientation, therefore should not be understood as limiting the present invention.
Referring to Fig.1-5, a kind of culvert vertical take-off and landing unmanned aerial vehicle, including fuselage 1, the two sides of fuselage 1 are symmetrically arranged with two
A wing 2, fuselage 1 are symmetrically arranged with two empennages 3 on one end far from wing 2, the of horizontal direction is equipped on two wings 2
Two ducts 5 are equipped with the first duct 4 of vertical direction at the center of fuselage 1, are equipped with duct in the first duct 4 and the second duct 5
Engine, the bottom side of fuselage 1 are equipped with front buffer device, and front buffer device is arranged far from empennage 3, and front buffer device includes
Support rod 6, support rod 6 are fixedly connected on the bottom side of fuselage 1.
One end of support rod 6 is fixedly connected with mounting plate 12, and the two sides of mounting plate 12 are fixedly connected to two and symmetrically set
The fixture block 13 set is fixedly connected with the fixed link 14 through fixture block 13 between two opposite fixture blocks 13, rotates in fixed link 14
It is connected with connecting rod 7, the two sides of connecting rod 7 are fixedly connected to torsional spring 15, and torsional spring 15 is fixedly connected far from one end of connecting rod 7
On fixture block 13, elastic telescopicing rod 17, connecting rod are rotatably connected to by symmetrically arranged limited block 16 between two connecting rods 7
7 one end far from fixture block 13 are equipped with front-wheel 8.
When fuselage 1 is during landing, and fuselage 1 is tilted because of the influence of the factors such as the wind-force of ambient enviroment, before two
One of them of wheel 8 is contacted with ground first, under the gravity of fuselage 1, is rotated with the front-wheel 8 that ground first contacts
The connecting rod 7 of connection is rotated around fixed link 14, and torsional spring 15 is driven to rotate, and the elastic force that torsional spring 15 generates reacts on connecting rod
7,7 one in rotational direction opposite elastic force of connecting rod are given, hinders connecting rod 7 to continue around fixed link 14 and is rotated, elastic force
Ground is acted on through connecting rod 7 and front-wheel 8, hinders the slope trend of fuselage 1.
In addition, connecting rod 7 will drive the elongation of elastic telescopicing rod 17 during rotation, to pass through elastic telescopicing rod 17
Elastic force plays the role of damping, and the bottom side of two wings 2 is equipped with postposition damping device, two postposition damping devices are close to
It fuselage 1 and is symmetrical set, postposition damping device includes damper 9, and damper 9 is fixedly connected on the bottom side of wing 2, damper
It is equipped with the first cavity 18 and the second cavity 19 in 9, is connected between the first cavity 18 and the second cavity 19 by through-hole, the second cavity
Restraining position ring block 22 is fixedly connected on 19 inner sidewall.
Stop collar 22 is arranged close to through-hole, slidably connects piston 20 in the first cavity 18, at the center of 20 bottom side of piston
It is fixedly connected with the mandril 10 through damper 9, mandril 10 is equipped with rear-wheel 11, front-wheel 8 and rear-wheel far from one end of piston 20
11 be wear-resisting rubber wheel, and elasticity is good and wear-resistant, can be used for a long time, fixed on the downside wall of the second cavity 19 to connect
It is connected to spring 23, one end of spring 23 is fixedly connected with sliding block 21, and sliding block 21 is slidably connected in the second cavity 19,20 He of piston
The surface of sliding block 21 is equipped with rubber membrane, can be improved the air-tightness in the first cavity 18 and the second cavity 19, subtracts to be promoted
The effect of shake.
The moment that fuselage 1 is fallen to the ground, rear-wheel 11 and ground face contact, fuselage 1 force the drive of wing 2 to subtract under the effect of gravity
Shake device 9 moves down, and mandril 10 and piston 20 are moved up with respect to the first cavity 18, under the extruding of piston 20, the first cavity
Air via through holes in 18 flow into the second cavity 19, and the first cavity 18 and the indoor air pressure of 19 chamber of the second cavity increase, air
It is compressed, preliminary damping is carried out to generated vibration in rear-wheel 11 and ground contact process, and convert the first sky for vibration
Air pressure change in chamber 18 and the second cavity 19, with the increase of air pressure, when in second chamber 19 air to the pressure of sliding block 21
When being greater than elastic force of the spring 23 to sliding block 21 with the gravity of sliding block 21 itself, sliding block 21 along the second cavity 19 inner sidewall to moving down
Dynamic, spring 23 is compressed, and the elastic force of spring 23 hinders the movement of sliding block 21 to go forward side by side row buffering, further progress damping.
In the utility model, aircraft is during landing, if fuselage 1 is landed with lateral attitude, two front-wheels 8
One of them contacted first with ground, under the gravity of fuselage 1,8 company of rotation of front-wheel that is first contacted with ground
The connecting rod 7 connect is rotated around fixed link 14, and torsional spring 15 is driven to rotate, and the elastic force that torsional spring 15 generates reacts on connecting rod 7,
7 one in rotational direction opposite elastic force of connecting rod are given, hinders connecting rod 7 to continue around fixed link 14 and is rotated, elastic force warp
Connecting rod 7 and front-wheel 8 act on ground, hinder the slope trend of fuselage 1, and are corrected to it；
Fuselage 1 lands moment, and rear-wheel 11 and ground face contact, fuselage 1 force wing 2 to drive damper 9 under the effect of gravity
It moves down, mandril 10 and piston 20 are moved up with respect to the first cavity 18, under the extruding of piston 20, in the first cavity 18
Air via through holes flow into the second cavity 19, and air is compressed, and convert vibration in the first cavity 18 and the second cavity 19
Air pressure change, with the increase of air pressure, when air is big to the gravity of the pressure and sliding block 21 itself of sliding block 21 in second chamber 19
When elastic force of the spring 23 to sliding block 21, sliding block 21 is moved down along the inner sidewall of the second cavity 19, and spring 23 is compressed, spring
23 elastic force hinders the movement of sliding block 21 to go forward side by side row buffering, further progress damping.
The preferable specific embodiment of the above, only the utility model, but the protection scope of the utility model is not
It is confined to this, anyone skilled in the art is within the technical scope disclosed by the utility model, practical according to this
Novel technical solution and its utility model design are subject to equivalent substitution or change, should all cover the protection model in the utility model
Within enclosing.
Claims (6)
1. a kind of culvert vertical take-off and landing unmanned aerial vehicle, including fuselage (1), which is characterized in that the two sides of the fuselage (1) are symmetrical
If being symmetrically arranged with two empennages (3), two machines on one end of the fuselage (1) separate wing (2) there are two wing (2)
It is equipped with the second duct (5) of horizontal direction on the wing (2), the first duct of vertical direction is equipped at the center of the fuselage (1)
(4), it is equipped with duct engine in first duct (4) and the second duct (5), the bottom side of the fuselage (1) is equipped with preposition
Buffer unit, the front buffer device are arranged far from empennage (3), and the bottom side of two wings (2) is equipped with postposition damping
Device, two postposition damping devices are close to fuselage (1) and are symmetrical set.
2. a kind of culvert vertical take-off and landing unmanned aerial vehicle according to claim 1, which is characterized in that the front buffer dress
It sets including support rod (6), the support rod (6) is fixedly connected on the bottom side of fuselage (1), and one end of the support rod (6) is fixed
It being connected with mounting plate (12), the two sides of the mounting plate (12) are fixedly connected to two symmetrically arranged fixture blocks (13), and two
It is fixedly connected with the fixed link (14) through fixture block (13) between the opposite fixture block (13), is rotated on the fixed link (14)
It is connected with connecting rod (7), the two sides of the connecting rod (7) are fixedly connected to torsional spring (15), and the torsional spring (15) is far from connection
One end of bar (7) is fixedly connected on fixture block (13), passes through symmetrically arranged limited block (16) between two connecting rods (7)
It is rotatably connected to elastic telescopicing rod (17), the connecting rod (7) is equipped with front-wheel (8) far from the one end of fixture block (13).
3. a kind of culvert vertical take-off and landing unmanned aerial vehicle according to claim 2, which is characterized in that the postposition damping dress
It sets including damper (9), the damper (9) is fixedly connected on the bottom side of wing (2), is equipped with first in the damper (9)
Cavity (18) and the second cavity (19) are connected between first cavity (18) and the second cavity (19) by through-hole, and described the
It slidably connects piston (20) in one cavity (18), is fixedly connected at the center of piston (20) bottom side through damper
(9) mandril (10), the mandril (10) are equipped with rear-wheel (11) far from the one end of piston (20), second cavity (19)
It is fixedly connected on downside wall spring (23), one end of the spring (23) is fixedly connected with sliding block (21), the sliding block (21)
It is slidably connected in the second cavity (19).
4. a kind of culvert vertical take-off and landing unmanned aerial vehicle according to claim 3, which is characterized in that second cavity
(19) it is fixedly connected on inner sidewall restraining position ring block (22), the stop collar (22) is arranged close to through-hole.
5. a kind of culvert vertical take-off and landing unmanned aerial vehicle according to claim 3, which is characterized in that the front-wheel (8) and
Rear-wheel (11) is wear-resisting rubber wheel.
6. a kind of culvert vertical take-off and landing unmanned aerial vehicle according to claim 3, which is characterized in that the piston (20) and
The surface of sliding block (21) is equipped with rubber membrane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821801590.8U CN209305826U (en) | 2018-11-02 | 2018-11-02 | A kind of culvert vertical take-off and landing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821801590.8U CN209305826U (en) | 2018-11-02 | 2018-11-02 | A kind of culvert vertical take-off and landing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209305826U true CN209305826U (en) | 2019-08-27 |
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ID=67672184
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821801590.8U Expired - Fee Related CN209305826U (en) | 2018-11-02 | 2018-11-02 | A kind of culvert vertical take-off and landing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209305826U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113184173A (en) * | 2021-06-07 | 2021-07-30 | 广西电网有限责任公司电力科学研究院 | VTOL fixed wing unmanned aerial vehicle with damping device |
| CN113212744A (en) * | 2021-06-07 | 2021-08-06 | 广西电网有限责任公司电力科学研究院 | Vertical take-off and landing fixed wing unmanned aerial vehicle with protection device |
-
2018
- 2018-11-02 CN CN201821801590.8U patent/CN209305826U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113184173A (en) * | 2021-06-07 | 2021-07-30 | 广西电网有限责任公司电力科学研究院 | VTOL fixed wing unmanned aerial vehicle with damping device |
| CN113212744A (en) * | 2021-06-07 | 2021-08-06 | 广西电网有限责任公司电力科学研究院 | Vertical take-off and landing fixed wing unmanned aerial vehicle with protection device |
| CN113212744B (en) * | 2021-06-07 | 2023-04-21 | 广西电网有限责任公司电力科学研究院 | Vertical take-off and landing fixed wing unmanned aerial vehicle with protection device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190827 Termination date: 20201102 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |